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公开(公告)号：US11480061B2
公开(公告)日：2022-10-25
申请号：US17151799
申请日：2021-01-19
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Thomas Raymond Farrell , Markus Feigl
Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
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公开(公告)号：US10822955B2
公开(公告)日：2020-11-03
申请号：US16235114
申请日：2018-12-28
Applicant: General Electric Company
Inventor： John McConnell Delvaux , Markus Feigl , Matthew Troy Hafner , Michael Anthony Wondrasek , James Zhang , Peter de Diego
Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral base and top portions. The airfoil may include a pin connector connecting the top portion to the base portion. The pin connector may include: a tab extending from the top portion; a complimentary slot for receiving the tab formed in the base portion; an elongated pin cavity formed through an interior region of the airfoil, where the pin cavity intersects the slot to divide the pin cavity into first and second pin cavity segments; a tab aperture formed through the tab, where the tab aperture is positioned so align with the pin cavity upon the tab being received within the slot; and a locking pin that extends continuously through the first segment of the pin cavity, the tab aperture, and the second segment of the pin cavity.
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公开(公告)号：US11339665B2
公开(公告)日：2022-05-24
申请号：US16816568
申请日：2020-03-12
Applicant: General Electric Company
Inventor： Andrew Clifford Hart , Jing Li , Suryarghya Chakrabarti , James Tyson Balkcum, III , Markus Feigl
Abstract: The present embodiments set forth a blade including an airfoil, the airfoil including a tip cap, a pressure sidewall and a suction sidewall extending axially between corresponding leading and trailing edges and radially between the base and the tip cap. The blade, including the airfoil and base, being formed in at least two airfoil parts, each of the two airfoil parts including contacting edges engaging each other respective contacting edges, the contacting edges defining a joint for preloading each of the at least two parts with each other and with the base. The at least two airfoil parts forming the airfoil being retained to each other by an interference fit at the joint. The interference fit providing frictional damping of vibrations in the blade during blade operation.
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公开(公告)号：US20210140328A1
公开(公告)日：2021-05-13
申请号：US17151799
申请日：2021-01-19
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Thomas Raymond Farrell , Markus Feigl
Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
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5.发明申请公开(公告)号：US20200256204A1
公开(公告)日：2020-08-13
申请号：US16270071
申请日：2019-02-07
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Thomas Raymond Farrell , Markus Feigl
IPC: F01D5/30
Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
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Patent Agency Ranking
公开(公告)号：US20210285330A1
公开(公告)日：2021-09-16
申请号：US16816568
申请日：2020-03-12
Applicant: General Electric Company
Inventor： Andrew Clifford Hart , Jing Li , Suryarghya Chakrabarti , James Tyson Balkcum, III , Markus Feigl
Abstract: The present embodiments set forth a blade including an airfoil, the airfoil including a tip cap, a pressure sidewall and a suction sidewall extending axially between corresponding leading and trailing edges and radially between the base and the tip cap. The blade, including the airfoil and base, being formed in at least two airfoil parts, each of the two airfoil parts including contacting edges engaging each other respective contacting edges, the contacting edges defining a joint for preloading each of the at least two parts with each other and with the base. The at least two airfoil parts forming the airfoil being retained to each other by an interference fit at the joint. The interference fit providing frictional damping of vibrations in the blade during blade operation.
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公开(公告)号：US10907484B2
公开(公告)日：2021-02-02
申请号：US16270071
申请日：2019-02-07
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Thomas Raymond Farrell , Markus Feigl
Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
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8.发明申请Method and System for Controlling Gas Turbine Performance With a Variable Backflow Margin 有权用于控制具有可变回流裕度的燃气轮机性能的方法和系统公开(公告)号：US20150059355A1
公开(公告)日：2015-03-05
申请号：US14018668
申请日：2013-09-05
Applicant: General Electric Company
Inventor： Markus Feigl , Gary Michael Itzel
Abstract: A system and method for controlling the performance of a gas turbine system is provided. A backflow margin pressure ratio for a component is determined. A modified backflow margin pressure ratio for the component is calculated based on the number of fired hours and starts. Bleed air along a first flow path is controlled based on the modified backflow margin pressure ratio.
Abstract translation: 提供了一种用于控制燃气轮机系统的性能的系统和方法。 确定组件的回流裕度压力比。 基于燃烧时间的数量计算组件的改进的回流裕度压力比，并启动。 基于改进的逆流裕度压力比来控制沿着第一流路的排出空气。
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公开(公告)号：US20200208528A1
公开(公告)日：2020-07-02
申请号：US16235114
申请日：2018-12-28
Applicant: General Electric Company
Inventor： John McConnell Delvaux , Markus Feigl , Matthew Troy Hafner , Michael Anthony Wondrasek , James Zhang , Peter de Diego
Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral base and top portions. The airfoil may include a pin connector connecting the top portion to the base portion. The pin connector may include: a tab extending from the top portion; a complimentary slot for receiving the tab formed in the base portion; an elongated pin cavity formed through an interior region of the airfoil, where the pin cavity intersects the slot to divide the pin cavity into first and second pin cavity segments; a tab aperture formed through the tab, where the tab aperture is positioned so align with the pin cavity upon the tab being received within the slot; and a locking pin that extends continuously through the first segment of the pin cavity, the tab aperture, and the second segment of the pin cavity.
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10.发明授权Method and system for controlling gas turbine performance with a variable backflow margin 有权用于控制燃气轮机性能的方法和系统具有可变的回流裕度公开(公告)号：US09366194B2
公开(公告)日：2016-06-14
申请号：US14018668
申请日：2013-09-05
Applicant: General Electric Company
Inventor： Markus Feigl , Gary Michael Itzel
Abstract: A system and method for controlling the performance of a gas turbine system is provided. A backflow margin pressure ratio for a component is determined. A modified backflow margin pressure ratio for the component is calculated based on the number of fired hours and starts. Bleed air along a first flow path is controlled based on the modified backflow margin pressure ratio.
Abstract translation: 提供了一种用于控制燃气轮机系统的性能的系统和方法。 确定组件的回流裕度压力比。 基于燃烧时间的数量计算组件的改进的回流裕度压力比，并启动。 基于改进的逆流裕度压力比来控制沿着第一流路的排出空气。
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